Download or read book Experimental Study of the Influence of the Boundary Layer Thickness on the Cavity Response in a Supersonic Flow written by Gregoire Boulard and published by . This book was released on 2010 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Study of Supersonic Cavity Flow Control with Vertical Rods written by Carolyn Leigh Thiemann and published by . This book was released on 2013 with total page 87 pages. Available in PDF, EPUB and Kindle. Book excerpt: Analysis of an open cavity shear layer when exposed to different leading edge pin configurations was studied experimentally, in a blow-down high speed wind tunnel run at Mach 1.84. A non-intrusive quantitative flow measurement system, Particle Image Velocimetry, was used to study velocity and vorticity fields with and without flow control implementations. The purpose of this study was to attempt to understand and explain the flow mechanisms which cause acoustic suppression obtained using different leading edge, vertical pin configurations. The cavity had an L/D of 4.89 and each pin configuration had a varied number and placement of pins, while pin height remained a constant 1⁄2 inch. The four configurations chosen to be studied were based on the best acoustic suppression results obtained by Milne [4]. To determine and understand the physical mechanism and source of attenuation of this type of cavity flow control technique, this study looked at the acoustic spectrum, velocity vector field data as well as the changes in the velocity and vorticity fields created by each pin configuration. It was determined that a redistribution of the velocity and diffusion of the vorticity in the boundary layer was caused by altering the characteristics of the boundary layer. Vertical pin configurations at the leading edge of a cavity resulted in flow characteristics which bring about a thickening of the shear layer which diffuses the boundary layer vorticity. Certain pin configurations result in various changes in the boundary layer velocity and vorticity redistributions, affecting the shear layer diffusing the boundary layer vorticity. Configurations using staggered pin patterns generated more effectively vorticity diffusion in the shear layer, which lowered the peaks and the broadband in the SPL spectrum. Possible configurations for future testing are also recommended to further study the flow suppression mechanisms.

Download or read book An experimental investigation of the turbulent boundary layer behind a forward facing step in supersonic flow written by Dave Robert Moore and published by . This book was released on 1958 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents the results of an experimental study of the effect of a disturbance, produced by a forward facing step, on the turbulent boundary layer in compressible flow. Boundary layer total pressure surveys and direct skin friction measurements were made at six stations on each of two test surfaces. One surface was smooth and the other surface had an 0.080-inch forward facing step. The test stations were all located downstream of the step, the height of which was approximately one-half the smooth surface boundary layer thickness. Data were obtained at Mach Numbers of 2.0, 2.5, 3.0, and 3.5 and the test Reynolds Numbers, based on momentum thickness, ranged from 8,000 to 10,000 approximately. The results of this investigation indicate that the effect of the disturbance, produced by the step on the 'law of the wall' and 'velocity defect law' profiles appears to be negligible from a point approximately 10 flat plate boundary layer thicknesses downstream from the step. (Author).

Download or read book Experimental Investigation of the Effects of a Diffusion Field on a Laminar Boundary Layer in Supersonic Flow written by S. William Gouse and published by . This book was released on 1957 with total page 286 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Laminar Boundary Layer on a Circular Cone in Supersonic Flow at a Small Angle of Attack written by Franklin K. Moore and published by . This book was released on 1951 with total page 710 pages. Available in PDF, EPUB and Kindle. Book excerpt: The laminar boundary layer on a circular cone at angle of attack to a supersonic stream is discussed. A perturbation analysis was made to show the influence of a small angle of attack on such boundary layer quantities as skin friction, boundary-layer thickness, viscous lift, drag, and pitching moment.

Download or read book An Introductory Guide to EC Competition Law and Practice written by Valentine Korah and published by . This book was released on 1994 with total page 2354 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 500 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of the Effect of Boundary layer Transition on the Average Heat Transfer to a Yawed Cylinder in Supersonic Flow written by Ivan E. Beckwith and published by . This book was released on 1956 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Investigation of the Turbulent Boundary Layer in Supersonic Flow Around Unyawed Cones with Small Heat Transfer and Correlations with Two Dimensional Data written by Walter Samuel Bradfield and published by . This book was released on 1957 with total page 344 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Research on Supersonic Turbulent Separated and Reattached Flows written by Seymour M. Bogdonoff and published by . This book was released on 1975 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: Basic research programs are reported with fundamental applications to supersonic flight. The experimental studies made use of the unique capabilities of the high Reynolds number Mach 3 facility. The experimental programs concentrated on phenomena associated with incipient separation and separation of turbulent boundary layers over a large Reynolds number range. The reattachment phenomena of a shear layer was also studied in great depth.

Download or read book Measurements of a Supersonic Favorable pressure gradient Turbulent Boundary Layer with Heat Transfer written by Robert L. P. Voisinet and published by . This book was released on 1973 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a detailed experimental investigation of the compressible turbulent boundary layer in a favorable-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall at momentum thickness Reynolds numbers from 6,700 to 56,000 and at three wall-to-adiabatic-wall temperature ratios. An attempt was made to hold values of Clauser's pressure-gradient parameter constant. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. (Modified author abstract).

Download or read book Theoretical Face Pressure and Drag Characteristics of Forward facing Steps in Supersonic Turbulent Boundary Layers written by D. K. Patel and published by . This book was released on 1975 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Investigation of Heat Transfer Effects on Boundary Layer Separation in Supersonic Flow written by G. E. Gadd and published by . This book was released on 1956 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1948 with total page 770 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Study of Highly Cooled Boundary Layer Transition and Heat Transfer in Supersonic Flow written by Hudson Lee Conley and published by . This book was released on 1971 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Approximate Turbulent Boundary layer Development in Plane Compressible Flow Along Thermally Insulated Surfaces with Application to Supersonic tunnel Contour Correction written by Maurice Tucker and published by . This book was released on 1950 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: As an application of the method, the contour correction of supersonic nozzles for the effects of boundary-layer development is discussed from the requirement of continuity of mass flow and from the requirement of expansion- and shock-wave elimination.

Download or read book NASA SP written by and published by . This book was released on 1992 with total page 654 pages. Available in PDF, EPUB and Kindle. Book excerpt: